High-temperature effect on continuous glass fiber reinforced polypropylene multilayer composite and corrugated sandwich panels  

作　　者：Shuyan NIE Xin PAN Liming CHEN Bing DU Jie WANG 

机构地区：[1]College of Aerospace Engineering,Chongqing University,Chongqing 400030,China [2]College of Material and New Energy,Chongqing University of Science and Technology,Chongqing 401331,China

出　　处：《Chinese Journal of Aeronautics》2025年第1期607-621,共15页中国航空学报(英文版)

基　　金：co-supported by the National Natural Science Foundation of China(Nos.12372127,12202085,12302464);the Fundamental Research Funds for the Central Universities,China(No.2024CDJXY009);the Chongqing Outstanding Youth Fund,China(No.CSTB2024NSCQ-JQX0028);the Chongqing Natural Science Foundation,China(Nos.cstc2021ycjh-bgzxm0117,CSTB2022NSCQ-MSX0608)。

摘　　要：The high-temperature mechanical behaviors of Multi-Layer Composite Panels(MCP)and Corrugated Sandwich Panels(CSP)of Continuous Glass Fiber-Reinforced Polypropylene(CGFRPP)are critical for their application in aerospace fields,which have been rarely mentioned in previous studies.High-temperature quasi-static tensile and compression tests on CGFRPP MCP are conducted first.The results showed that the tensile and compression strength,stiffness,and tensile modulus of MCP decreased with increasing temperature.The Gibson model was found to be more suitable for predicting the high-temperature mechanical performance of MCP after comparing the calculated results of different theoretical models with experimental data.Secondly,hightemperature planar compression tests were conducted on the CGFRPP CSP,revealing that the main failure modes were corrugated core buckling and delamination between the face panel and core material,with delamination being intensified at higher temperatures.Therefore,we proposed a strength theoretical model that considers structural buckling failure and interface delamination failure,and introduced the influence factor to evaluate the effect of interface delamination on structural strength.

关 键 词：High-temperature effect Fiber reinforced plastic Composite structure Sandwich structure Interface delamination Strength theory 

分 类 号：V258.3[一般工业技术—材料科学与工程] TB332[航空宇航科学与技术—航空宇航制造工程]